平流层飞艇空气动力估算

Aerodynamic Estimation for Stratosphere Airship

本文采用有限基本解方法与工程估算方法相结合的气动力工程计算方法,用以计算平流层飞艇的气动力。将飞艇所受的气动力分成飞艇艇身和尾翼所受气动力两部分,每一部分的气动力按照无粘性流产生的线性气动力和粘性引起的非线性气动力分别进行计算。根据势流理论对飞艇艇身线性气动力进行分析计算,由于飞艇艇体是旋成体,故根据Allen的横流阻力理论对其所受的非线性气动力进行计算;尾翼的线性气动力采用有限基本解方法进行计算,非线性气动力用Polhamus-Lamar吸力比拟方法估算。该方法中考虑了由于尾翼安装在体上后,处于艇体产生的上洗流场中,尾翼气动力的变化和尾翼对艇身气动力的干扰作用。通过算例的计算与实验结果比较得出该方法可以快速、准确的计算飞艇所受的气动力。

An efficient aerodynamic calculation method, based on a panel method and engineering estimation approach was used. The aerodynamic forces of airship are divided into two part： the aerodynamic forces of airship body and fins. Every part is composed of the linear and nonlinear aerodynamic forces. The linear aerodynamic forces of airship hull were calculated in terms of Munk airship theory. The linear aerodynamic forces of airship hull were calculated by Allen viscous cross flow theory. The fins linear aerodynamic forces were calculated by approach of panel method. The nonlinear aerodynamic forces of fins were calculated by Polhamus-Lamar suction analogy method. The interference of body and fins are included in this model. It shows that the model can efficient estimate the aerodynamic forces of airship through the comparison of results between computation and experiment.